ANALYSIS OF PRESSURE DISTRIBUTION ON THE SONDA III VEHICLE IN TRANSONIC REGIME

M. L. C. C. Reis, J. B. P. F. Filho, E. Basso, J. D. Costa

Abstract

A half model of the aerospace vehicle Sonda III is being tested at the Brazilian Pilot Transonic Wind Tunnel. The aim of the tests is to study the presence of shock and expansion waves in the inter-stage region of the vehicle. Special emphasis is placed on the nominal Mach number 0.90. Measured values are static pressure on the model surface and freestream total and static pressures. The estimated parameters are pressure coefficients and Mach number. Numerical analysis of the flow field parameters is done and compared to experimental results.

Keywords

shock waves, uncertainty in measurements, sounding rocket, transonic wind tunnel

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IMEKO-WC-2015-TC7-198.pdf

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IMEKO TC

TC7 - Measurement Science

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